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Introduction

Spacecraft structural designs have to be designed and verified for a number of mechanical environments, namely:

Quasi-static loads

Sinusoidal vibration

Acoustic Noise

Shock

The environments are present during launch or due to activation of spacecraft equipment. The paper presents the Structural Thermal Model (STM) acoustic test prediction vibration analysis performed in the frame of the SGEO satellite project and the analysis correlation to STM test results.

For the analysis the same Finite Element Model (FEM) as for the sinusoidal vibration analysis has been used. Then the FEM has been exposed to an acoustic field using the boundary element method (BEM) based on the program code Rayon, which is included in the vibro-acoustic pre/post processor VA One.

Analysis results have been compared with STM test results and a very good correlation as well as confirmation of the baseline assumptions has been found.